Propagator
, PVCoordinatesProvider
AdapterPropagator
, AggregateBoundedPropagator
, EcksteinHechlerPropagator
, Ephemeris
, GPSPropagator
, IntegratedEphemeris
, KeplerianPropagator
, TLEPropagator
public abstract class AbstractAnalyticalPropagator extends AbstractPropagator
Propagator
methods for analytical propagators.
This abstract class allows to provide easily the full set of Propagator
methods, including all propagation
modes support and discrete events support for any simple propagation method. Only
two methods must be implemented by derived classes: propagateOrbit(AbsoluteDate)
and getMass(AbsoluteDate)
. The first method should perform straightforward
propagation starting from some internally stored initial state up to the specified target date.
DEFAULT_LAW, DEFAULT_MASS, EPHEMERIS_GENERATION_MODE, MASTER_MODE, SLAVE_MODE
Modifier | Constructor | Description |
---|---|---|
protected |
AbstractAnalyticalPropagator(AttitudeProvider attitudeProvider) |
Build a new instance.
|
Modifier and Type | Method | Description |
---|---|---|
protected SpacecraftState |
acceptStep(OrekitStepInterpolator interpolator,
AbsoluteDate target,
double epsilon) |
Accept a step, triggering events and step handlers.
|
<T extends EventDetector> |
addEventDetector(T detector) |
Add an event detector.
|
protected SpacecraftState |
basicPropagate(AbsoluteDate date) |
Propagate an orbit without any fancy features.
|
void |
clearEventsDetectors() |
Remove all events detectors.
|
Collection<EventDetector> |
getEventsDetectors() |
Get all the events detectors that have been added.
|
BoundedPropagator |
getGeneratedEphemeris() |
Get the ephemeris generated during propagation.
|
protected abstract double |
getMass(AbsoluteDate date) |
Get the mass.
|
PVCoordinatesProvider |
getPvProvider() |
Get PV coordinates provider.
|
SpacecraftState |
propagate(AbsoluteDate start,
AbsoluteDate target) |
Propagate from a start date towards a target date.
|
protected abstract Orbit |
propagateOrbit(AbsoluteDate date) |
Extrapolate an orbit up to a specific target date.
|
protected abstract void |
resetIntermediateState(SpacecraftState state,
boolean forward) |
Reset an intermediate state.
|
addAdditionalStateProvider, getAdditionalStateProviders, getAttitudeProvider, getFixedStepSize, getFrame, getInitialState, getManagedAdditionalStates, getMode, getPVCoordinates, getStartDate, getStepHandler, isAdditionalStateManaged, propagate, resetInitialState, setAttitudeProvider, setEphemerisMode, setEphemerisMode, setMasterMode, setMasterMode, setSlaveMode, setStartDate, updateAdditionalStates
protected AbstractAnalyticalPropagator(AttitudeProvider attitudeProvider)
attitudeProvider
- provider for attitude computationpublic BoundedPropagator getGeneratedEphemeris()
getGeneratedEphemeris
in interface Propagator
getGeneratedEphemeris
in class AbstractPropagator
Propagator.setEphemerisMode()
public <T extends EventDetector> void addEventDetector(T detector)
addEventDetector
in interface Propagator
addEventDetector
in class AbstractPropagator
T
- class type for the generic versiondetector
- event detector to addPropagator.clearEventsDetectors()
,
Propagator.getEventsDetectors()
public Collection<EventDetector> getEventsDetectors()
getEventsDetectors
in interface Propagator
getEventsDetectors
in class AbstractPropagator
Propagator.addEventDetector(EventDetector)
,
Propagator.clearEventsDetectors()
public void clearEventsDetectors()
clearEventsDetectors
in interface Propagator
clearEventsDetectors
in class AbstractPropagator
Propagator.addEventDetector(EventDetector)
,
Propagator.getEventsDetectors()
public SpacecraftState propagate(AbsoluteDate start, AbsoluteDate target)
Those propagators use a start date and a target date to compute the propagated state. For propagators using event detection mechanism, if the provided start date is different from the initial state date, a first, simple propagation is performed, without processing any event computation. Then complete propagation is performed from start date to target date.
start
- start date from which orbit state should be propagatedtarget
- target date to which orbit state should be propagatedprotected SpacecraftState acceptStep(OrekitStepInterpolator interpolator, AbsoluteDate target, double epsilon) throws org.hipparchus.exception.MathRuntimeException
interpolator
- interpolator for the current steptarget
- final propagation timeepsilon
- threshold for end date detectionorg.hipparchus.exception.MathRuntimeException
- if an event cannot be locatedprotected abstract double getMass(AbsoluteDate date)
date
- target date for the orbitpublic PVCoordinatesProvider getPvProvider()
protected abstract void resetIntermediateState(SpacecraftState state, boolean forward)
state
- new intermediate state to considerforward
- if true, the intermediate state is valid for
propagations after itselfprotected abstract Orbit propagateOrbit(AbsoluteDate date)
date
- target date for the orbitprotected SpacecraftState basicPropagate(AbsoluteDate date)
This method is similar in spirit to the propagate(org.orekit.time.AbsoluteDate, org.orekit.time.AbsoluteDate)
method,
except that it does not call any handler during
propagation, nor any discrete events, not additional states. It always
stop exactly at the specified date.
date
- target date for propagationCopyright © 2002-2019 CS Systèmes d'information. All rights reserved.